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PROPOSED AD GA 8 AIRVAN (PTY) LTD: Docket No. FAA-2024-0035; Project Identifier MCAI-2023-00986-A.
(a) COMMENTS DUE DATE

    The FAA must receive comments on this airworthiness directive (AD)  by
    March 8, 2024.

(b) AFFECTED ADS

    This AD replaces AD 2010-18-06,Amendment 39-16419 (75 FR 52253, August
    25, 2010).

(c) APPLICABILITY

    This AD applies to GA 8 Airvan (Pty) Ltd  Model GA8 and GA8-TC320 air-
    planes, all serial numbers, certificated in any category.

(d) SUBJECT

    Joint Aircraft System Component (JASC) Code 5230, Cargo/Baggage Doors.

(e) UNSAFE CONDITION

    This AD was  prompted by reports  of in-flight cargo  door separation.
    The FAA is issuing this AD to detect and correct excessive wear in the
    forward  cargo  door  slide,  which  could  result  in  an   in-flight
    separation of  the cargo  door, with  possible loss  of control of the
    airplane.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) REQUIRED ACTIONS

    Do the applicable  actions  specified  in  Table 1 to paragraph (g) of
    this AD at the times  in Table 1  to  paragraph (g)  of  this  AD,  in
    accordance  with the Accomplishment Instructions  of GippsAero Service
    Bulletin SB-GA8-2005-23,  Issue 8,  dated  October 11, 2023 (GippsAero
    SB-GA8-2005-23, Issue 8).

                            TABLE 1 TO PARAGRAPH (G)                      
    ______________________________________________________________________
    PARAGRAPHS IN ACCOMPLISHMENT
    INSTRUCTIONS OF GIPPSAERO              ACTION          COMPLIANCE TIME
    SB-GA8-2005-23, ISSUE 8
    ______________________________________________________________________
    12.1, A1, steps 1 and 2, for      Inspect for the    Inspect within 50
    backing plate inspection,         existence of a     hours time-in-
    except where Figure 1 in step 1   backing plate on   service (TIS) or
    specifies to remove and discard   the forward slide  2 months after
    the vertical bolt, remove the     of the cargo       the effective
    vertical bolt from service.       door. If a         date of this AD,
                                      backing plate is   whichever occurs
                                      not installed,     first. Install,
    Steps 3 through 7, if a backing   install a backing  measure, and
    plate is not installed.           plate on the       replace before
                                      forward slide of   further flight
                                      the cargo door,    after the
                                      measure the        inspection.
                                      groove width of
                                      the forward
                                      slide, and
                                      replace the slide
                                      if it exceeds
                                      0.145 inch at any
                                      point or is
                                      cracked or worn
                                      beyond limits.

    12.2, A2, steps 1 and 2 for the   Inspect for wear   Inspect for wear
    inspection.                       of the forward     within 100 hours
                                      slide of the       TIS or 2 months
                                      cargo door by      after the
    12.2, A2, step 3 or 4, and 12.1,  inserting a slide  effective date of
    A1, steps 2 through 4, for the    gauge or feeler    this AD,
    follow-on inspection and          gauge to measure   whichever occurs
    replacement.                      the clearance      first, and
                                      between the        thereafter at
                                      forward slide and  intervals not to
                                      the cargo door     exceed 100 hours
                                      track. If a gap    TIS or 12 months,
                                      is found, measure  whichever occurs
                                      the groove width   first after the
                                      of the forward     most recent
                                      slide and replace  inspection.
                                      the slide if the   Measure the
                                      groove width       groove width and
                                      exceeds 0.145      replace the slide
                                      inch at any point  before further
                                      or is cracked or   flight after each
                                      worn beyond        inspection as
                                      limits.            necessary.

    12.3, B1, steps 1 through 6 for   Inspect the cargo  Inspect within 50
    the inspections.                  door mechanism     hours TIS or 2
                                      for contact        months after the
                                      between the        effective date of
    12.3, B1, steps 2, 3i, and 3ii;   operating rod and  this AD,
    12.4, B2, steps 1 through 5;      cargo door handle  whichever occurs
    and 12.5, B3, steps 1 through     pivot post,        first and
    12 for the corrective actions.    inspect the        thereafter at
                                      threaded studs     intervals not to
                                      and rod ends at    exceed 100 hours
                                      both ends of the   TIS or 12 months,
                                      operating rod for  whichever occurs
                                      bending, and       first after the
                                      inspect the cargo  most recent
                                      door handle        inspection.
                                      engagement with    Perform all
                                      the catch.         applicable
                                      Perform all        corrective
                                      applicable         actions before
                                      corrective         further flight.
                                      actions.

    12.6, C, steps 1 through 6        Inspect the cargo  Within 150 hours
                                      door handle to     TIS or 4 months
                                      determine if an    after the
                                      integrated stop    effective date of
                                      is installed and   this AD,
                                      if an integrated   whichever occurs
                                      stop is not        first. Perform
                                      installed,         the installation
                                      install a cargo    and replacement,
                                      door handle with   as necessary,
                                      an integrated      before further
                                      stop. Inspect the  flight after the
                                      cargo door handle  inspection.
                                      for beyond normal
                                      play and replace
                                      the handle bush
                                      if the door
                                      handle has beyond
                                      normal play.

    12.7, D1, steps 1 through 10 for  Inspect the center Within 50 hours
    the center rail cargo door        rail of the cargo  TIS or 2 months
    inspection and installation.      door to determine  after the
                                      if a center rail   effective date of
                                      aft stop is        this AD,
    12.8, D2, steps 1 through 2, for  installed and if   whichever occurs
    any necessary follow-on rework.   a center rail aft  first.
                                      stop is not
                                      installed,
                                      install an aft
                                      stop before
                                      further flight.
    ______________________________________________________________________

(h) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

    The Manager, International Validation  Branch, FAA, has the  authority
    to approve AMOCs for this AD, if requested using the procedures  found
    in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to
    your principal inspector or local Flight Standards District Office, as
    appropriate. If  sending information  directly to  the manager  of the
    International Validation Branch, mail it to the address identified  in
    paragraph (i)(2) of this  AD or email to:  9-AVS-AIR-730-AMOC@faa.gov.
    If mailing information, also submit information by email. Before using
    any approved  AMOC, notify  your appropriate  principal inspector,  or
    lacking  a  principal  inspector,  the  manager  of  the  local Flight
    Standards District Office/certificate holding district office.

(i) ADDITIONAL INFORMATION

(1) Refer to Civil Aviation Safety Authority (CASA)  Australia AD AD/GA8/3
    amdt 3, dated August 18, 2023,  for  related  information.  This  CASA
    Australia AD may be found in the AD docket  at  regulations.gov  under
    Docket No. FAA-2024-0035.

(2) For more information  about this AD,  contact  Doug Rudolph,  Aviation
    Safety Engineer,  FAA,  1600 Stewart Avenue,  Suite 410,  Westbury, NY
    11590; phone: (816) 329-4059; email: doug.rudolph@faa.gov.

(j) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference  (IBR)  of the service information  listed in this paragraph
    under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable  to do the actions
    required by this AD, unless the AD specifies otherwise.

(i) GippsAero Service Bulletin SB-GA8-2005-23, Issue 8,  dated October 11,
    2023.

(ii) [Reserved]

(3) For service information identified in this AD contact GA8 Airvan (Pty)
    Ltd, PO Box 881, Morwell, Victoria 3840, Australia; phone: +61 03 5172
    1200; website: gippsaero.com.au; email: TECHPUBS@gippsaero.com.au.

(4) You may view this service information at the FAA,  Airworthiness Prod-
    ucts Section, Operational Safety Branch,  901 Locust,  Kansas City, MO
    64106. For information on the availability of this material at the FAA
    call (817) 222-5110.

(5) You may view this material at the National Archives and Records Admin-
    istration (NARA). For information on the availability of this material
    at NARA,  visit www.archives.gov/federal-register/cfr/ibr-locations or
    email fr.inspection@nara.gov.

Issued on January 12, 2024. Victor Wicklund, Deputy Director, Compliance &
Airworthiness Division, Aircraft Certification Service.

DATES: The FAA must receive comments on this NPRM by March 8, 2024.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-0035; Project Identifier MCAI-2023-00986-A]
RIN 2120-AA64

Airworthiness Directives; GA 8 Airvan (Pty) Ltd Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2010-18-06, which applies to all GA8 Airvan (Pty) Ltd Model GA8 and
GA8-TC320 airplanes. AD 2010-18-06 requires inspections and a minor
design change to the forward slide of the cargo door with corrective
action as necessary. Since the FAA issued AD 2010-18-06, the Civil
Aviation Safety Authority (CASA), which is the aviation authority for
Australia, superseded the previous CASA Australia AD to incorporate
more detailed inspections and additional modifications as specified in
updated service information published by the manufacturer. This
proposed AD was prompted by reports of in-flight cargo door separation.
This proposed AD would require inspections and rework (modifications)
of the cargo door with corrective action as necessary. The FAA is
proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this NPRM by March 8, 2024.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2024-0035; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this NPRM, the mandatory continuing airworthiness
information (MCAI) any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
For service information identified in this NPRM, contact
GA8 Airvan (Pty) Ltd, PO Box 881, Morwell, Victoria 3840, Australia;
phone: +61 03 5172 1200; website: gippsaero.com.au; email:
gippsaero.com.au">TECHPUBS@gippsaero.com.au.
You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 901 Locust,
Kansas City, MO 64106. For information on the availability of this
material at the FAA, call (817) 222-5110.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (816) 329-4059; email: doug.rudolph@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2024-0035; Project Identifier
MCAI-2023-00986-A'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.

Confidential Business Information

CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Doug
Rudolph, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590. Any commentary that the FAA receives which is not
specifically designated as CBI will be placed in the public docket for
this rulemaking.

Background

The FAA issued AD 2010-18-06, Amendment 39-16419 (75 FR 52253,
August 25, 2010) (AD 2010-18-06), for all GA8 Airvan (Pty) Ltd Model
GA8 and GA8-TC320 airplanes. AD 2010-18-06 was prompted by MCAI
originated by CASA, which is the aviation authority for Australia. CASA
Australia issued CASA Australia AD AD/GA8/3 Amdt 2, dated August 11,
2010 (CASA Australia AD/GA8/3 Amdt 2) to correct an unsafe condition
identified as excessive wear in the forward cargo door slide, which
could result in an in-flight separation of the cargo door, with
possible loss of control of the airplane. CASA Australia AD AD/GA8/3
Amdt 2 was issued to require the actions in service information updated
by the manufacturer to remove any ambiguities in the previous revision
and provide an improved inspection method and a minor design change to
the forward slide of the cargo door (inclusion of a slide backing
plate, castellated nut, and split pin).
AD 2010-18-06 requires doing all of Action 1 (measuring the groove
width of the forward cargo door slide and if it exceeds 0.145 inch at any point
along the slide, or is cracked, installing a new slider assembly) and
Action 2 (inspecting wear of the forward slide of the cargo door and
doing applicable corrective action steps specified in Action 1) of
GippsAero Pty. Ltd. Mandatory Service Bulletin SB-GA8-2005-23, Issue 3,
dated August 5, 2010. The FAA issued AD 2010-18-06 to address excessive
wear in the forward cargo door slide.

Actions Since AD 2010-18-06 Was Issued

Since the FAA issued AD 2010-18-06, CASA Australia superseded CASA
Australia AD AD/GA8/3 Amdt 2 and issued CASA Australia AD AD/GA8/3 Amdt
3, dated August 18, 2023 (CASA Australia AD AD/GA8/3 Amdt 3) (also
referred to as the MCAI). The MCAI states that inspections revealed
cases of excessive wear in the forward slide of the cargo door.
Excessive wear in the forward slide of the cargo door may result in the
cargo door separating from the airplane in flight with potentially
catastrophic results. The MCAI requires accomplishing the actions
specified in GippsAero Service Bulletin SB-GA8-2005-23, Issue 7, dated
May 30, 2023 (GippsAero Service Bulletin SB-GA8-2005-23, Issue 7). This
service bulletin includes procedures for revised inspections of the
door mechanism, installing a stop on the forward slide of the cargo
door and reworking the door slide to suit (accommodate) the track stop
installation. Depending on the findings of the inspections, additional
actions might be necessary including reworking the door mechanism
pivot, upgrading the door operating rod, or fitting a door handle with
an integral stop.
The FAA is proposing this AD to address excessive wear in the
forward slide of the cargo door. The unsafe condition, if not
addressed, could result in the cargo door separating from the airplane
during flight, with potential loss of control of the airplane.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2024-0035.

Related Service Information Under 1 CFR Part 51

The FAA reviewed GippsAero Service Bulletin SB-GA8-2005-23, Issue
8, dated October 11, 2023 (GippsAero SB-GA8-2005-23, Issue 8). This
service information specifies procedures for installing a backing plate
on the forward slide of the cargo door; inspecting the forward slide of
the cargo door for excessive wear; inspecting the cargo door latching
mechanism for contact between the operating rod and door handle pivot
post, inspecting the threaded studs and rod ends at both ends of the
operating rod for bending, and checking the cargo door handle
engagement with the catch; reworking the cargo door handle pivot post;
reworking the door operating rod; inspecting the door handle to
determine if an integrated stop is installed and checking for excessive
play; and inspecting the center rail of the cargo door to determine if
an aft stop is installed, installing an aft stop, and reworking the
center rail of the cargo door to accommodate the track stop.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in ADDRESSES.

FAA's Determination


These products have been approved by the aviation authority of
another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with this State of Design
Authority, it has notified the FAA of the unsafe condition described in
the MCAI and service information referenced above. The FAA is issuing
this NPRM after determining that the unsafe condition described
previously is likely to exist or develop on other products of the same
type design.

Proposed AD Requirements in This NPRM

This proposed AD would retain none of the requirements of AD 2010-
18-06. This proposed AD would require accomplishing the actions
specified in the service information already described, except as
discussed under ``Differences Between this Proposed AD and the MCAI.''

Differences Between This Proposed AD and the MCAI

The MCAI applicability is Gippsland Aeronautics Model GA8 Series
airplanes, all serial numbers. The applicability in this proposed AD
would be GA8 Airvan (Pty) Ltd Model GA8 and GA8-TC320 airplanes because
the FAA type certificate specifies GA8 Airvan (Pty) Ltd instead of
Gippsland Aeronautics and specifies Model GA8 and GA8-TC320 airplanes
instead of Model GA8 Series airplanes.
The MCAI requires doing the actions in Gippsland Aeronautics
mandatory service bulletin SB-GA8-2005-23 Issue 7, dated May 30, 2023.
This proposed AD would require doing the actions in GippsAero SB-GA8-
2005-23, Issue 8. After the MCAI was published, the manufacturer issued
GippsAero SB-GA8-2005-23, Issue 8, which was revised to provide
clarification regarding the actions and compliance schedule. The title
page of GippsAero SB-GA8-2005-23, Issue 8, specifies GippsAero instead
of Gippsland Aeronautics.

Costs of Compliance

The FAA estimates that this AD, if adopted as proposed, would
affect 61 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD. The corresponding letter and number in parenthesis refer to the
specific paragraph in GippsAero SB-GA8-2005-23, Issue 8.

Estimated Costs

Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Installing forward cargo door slide backing plate (A1) 0.50 work-hour x $85 per hour = $42.50
$175
$217.50 $13,267.50
Inspecting forward cargo door slide wear (A2) 0.25 work-hour x $85 per hour = $21.25 per inspection cycle
0
21.25 per inspection cycle 1,296.25 per inspection cycle
Inspecting cargo door latching mechanism (B1) 1 work-hour x $85 per hour = $85 per inspection cycle
0
85 per inspection cycle 5,185 per inspection cycle
Inspecting cargo door handle and inspecting for excessive play (C) 0.75 work-hour x $85 per hour = $63.75
0
63.75 388.75
Inspecting cargo door center rail (D1) 1 work-hour x $85 per hour = $85
0
85 5,185

The FAA estimates the following costs to do any necessary actions
that would be required based on the results of the proposed
inspections. The agency has no way of determining the number of
airplanes that might need these actions. The corresponding letter and
number in parenthesis refer to the specific paragraph in GippsAero SB-
GA8-2005-23, Issue 8.

On-Condition Costs

Action
Labor cost
Parts cost
Cost per product
Inspecting/replacing forward cargo door slide (A1, Steps 2 through 4), corrective action for (A2) 0.50 work-hour x $85 per hour = $42.50
$175
$217.50
Reworking cargo door pivot (B2) and reworking/replacing door operating rod assembly (B3) 2 work-hours x $85 per hour = $170
630
800
Replacing door handle/handle bush (C) 1 work-hour x $85 per hour = $85
267
352
Replacing cargo door center rail/slide-center and backing plate (D1) and reworking cargo door center rail and backing plate (D2) 2 work-hours x $85 per hour = $170
152
322

The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected operators.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings

The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by:

a. Removing Airworthiness Directive 2010-18-06, Amendment 39-16419 (75
FR 52253, August 25, 2010); and

b. Adding the following new airworthiness directive: